Method and system for providing cooling for turbine components

Patent metadata

Field	Value
Publication number	US-9458725-B2
Application number	US-201314046437-A
Country	US
Kind code	B2
Filing date	Oct 4, 2013
Priority date	Oct 4, 2013
Publication date	Oct 4, 2016
Grant date	Oct 4, 2016

Abstract

A method and system for providing cooling of a turbine component that includes a region to be cooled is provided. A recess is defined within the region to be cooled, and includes an inner face. At least one support projection extends from the inner face. The at least one support projection includes a free end. A cover is coupled to the region to be cooled, such that an inner surface of the cover is coupled to the free end of the at least one support projection, such that at least one cooling fluid passage is defined within the region to be cooled.

First claim

What is claimed is:

1. A method for providing a cooling system for a turbine component, wherein said method comprises:
defining a turbine component body, wherein the turbine component body includes a region to be cooled;
defining a recess within the region to be cooled, wherein the recess includes an inner face;
defining at least one support projection extending from the inner face, wherein the at least one support projection includes a free end;
coupling a cover to the region to be cooled, such that an inner surface of the cover is coupled to the free end of the at least one support projection, to define at least one cooling passage within the region to be cooled; and
coupling at least one of a bond coat and a thermal barrier coat to the cover.

2. A method in accordance with claim 1 , wherein said method comprises coupling the at least one cooling passage within the region to be cooled in flow communication with a source of cooling fluid.

3. A method in accordance with claim 1 , wherein defining a recess within the region to be cooled comprises:
removing a volume of sacrificial material from the region to be cooled, wherein the region to be cooled extends from a tip of a trailing-edge region of the turbine component body to a location spaced a distance from the trailing-edge tip; and
defining a shoulder at the location spaced a distance from the trailing-edge tip.

4. A method in accordance with claim 1 , wherein defining at least one support projection comprises defining the at least one support projection to extend from the inner face in a direction substantially perpendicular to the inner face of the recess.

5. A method in accordance with claim 1 , wherein defining at least one support projection comprises defining a plurality of support projections extending from the inner face.

6. A method in accordance with claim 1 , wherein coupling a cover comprises:
locating a layer of braze material in juxtaposition with the free end of the at least one support projection; and
heating the braze material and the component body such that the layer of braze material couples to the free end of the at least one support projection.

7. A method in accordance with claim 6 , wherein said method comprises coupling the bond coat to the layer of braze material.

8. A method in accordance with claim 7 , wherein said method comprises coupling the thermal barrier coat to the bond coat.

9. A method in accordance with claim 1 , wherein defining at least one support projection extending from the inner face comprises one of:
selectively removing material from the region to be cooled to define at least one pin; and
positioning a layer of porous metal foam material within the recess.

10. A system for providing cooling of a turbine component, said system comprising:
a turbine component body that includes a region to be cooled;
a recess defined within said region to be cooled, wherein said recess includes an inner face;
at least one support projection extending from said inner face, wherein said at least one support projection includes a free end;
a cover coupled to said region to be cooled, such that an inner surface of said cover is coupled to said free end of said at least one support projection, such that at least one cooling fluid passage is defined within said region to be cooled; and
at least one of a bond coat and a thermal barrier coat coupled to said cover.

11. A system in accordance with claim 10 , wherein said system comprises a source of cooling fluid coupled to said at least one cooling fluid passage.

12. A system in accordance with claim 10 , wherein said recess comprises:
said inner face extending from a tip of a trailing-edge region to a location spaced a distance from said trailing-edge tip; and
a shoulder defined at said location spaced a distance from said trailing-edge tip.

13. A system in accordance with claim 10 , wherein said at least one support projection extends from said inner face in a direction substantially perpendicular to said inner face.

14. A system in accordance with claim 10 , wherein said at least one support projection comprises a plurality of support projections extending from said inner face.

15. A system in accordance with claim 10 , wherein said cover comprises a layer of braze material coupled to said free end of said at least one support projection.

16. A system in accordance with claim 15 , wherein said system comprises said bond coat coupled to said layer of braze material.

17. A system in accordance with claim 16 , wherein said system comprises said thermal barrier coat coupled to said bond coat.

18. A gas turbine system, said gas turbine system comprising:
a compressor section;
a combustion system coupled in flow communication with said compressor section; and
a turbine section coupled in flow communication with said combustion system, wherein said turbine section comprises:
an airfoil of a turbine component, said airfoil comprising a surface positioned to be in contact with a hot gas flow path of said gas turbine system, said airfoil further comprising a region to be cooled adjacent to said surface;
a recess defined within said region to be cooled, wherein said recess includes an inner face;
at least one support projection extending from said inner face, wherein said at least one support projection includes a free end; and
a cover coupled to said region to be cooled of said turbine component body, such that an inner surface of said cover is coupled to said free end of said at least one support projection, such that at least one cooling fluid passage is defined within said region to be cooled.

19. A system in accordance with claim 18 , wherein said recess comprises:
said inner face extending from a tip of a trailing-edge region to a location spaced a distance from said trailing-edge tip; and
a shoulder defined at said location spaced a distance from said trailing-edge tip.

20. A system in accordance with claim 18 , wherein said system comprises at least one of a bond coat and a thermal barrier coat coupled to said cover.

Assignees

• Gen Electric

Inventors

• Morgan Victor John
• Harris Jr John Wesley
• Healy Michael James
• Smith Aaron Ezekiel
• Brzek Brian Gene
• Floyd Ii Donald Earl

Classifications

• F05D2260/202

  by film cooling · CPC title

• F05D2230/90

  Coating; Surface treatment · CPC title

• F05D2260/22141

  using fins or ribs · CPC title

• F01D5/186

  Film cooling (F01D5/187 takes precedence) · CPC title

• F05D2230/21

  by casting · CPC title